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为研究采用多支柱小车式起落架布局的飞机在地面操纵特性并提出相关设计指标,建立了一套动力学分析模型,求出采用多支柱小车式起落架布局飞机的许用前轮偏转角的通解。通过仿真计算求得前轮许用偏转角度相关特性,通过试验验证了上述理论研究的正确性与合理性。经研究:多支柱小车式起落架许用前轮转弯角度主要受飞机速度等因素影响;在不改变飞机构型、不影响飞机性能及安全性的前提下,可通过降低飞机速度及减小前轮偏转角度提高飞机地面运动稳定性;在飞机速度一定时,将前轮偏转角度控制在许用包线内,则飞机转弯时不会发生侧翻;前轮转弯控制律设计过程中,可通过使控制律曲线尽量贴近许用包线以提高飞机地面操纵机动性。
In order to study the maneuvering characteristics of the aircraft using multi-pillar dolly landing gear and to propose relevant design indexes, a set of dynamic analysis model was established and the allowable front wheel deflection angle of the aircraft using multi-pillar dolly landing gear was obtained General solution. Through the simulation calculation, the relevant characteristics of the front wheel allowable deflection angle are obtained. The correctness and rationality of the theoretical research above are verified through experiments. The study: Multi-pillar small car landing gear allows the front wheel angle of rotation is mainly affected by aircraft speed and other factors; without changing the aircraft configuration, does not affect the aircraft’s performance and safety premise, by reducing the aircraft speed and reduce the front Wheel deflection angle to improve the stability of the ground movement of the aircraft; at a certain speed, the front wheel deflection angle control in the allowable envelope, the aircraft will not turn when cornering; front wheel steering control design process, by Make the control law curve as close to the allowable envelope as possible to improve the maneuverability of the aircraft ground.